Damping structure, gimbal assembly, and unmanned aerial vehicle

ABSTRACT

A damping structure configured for connecting a gimbal with a carrier includes a first connecting member connectable with the gimbal, a second connecting member connectable with the carrier, and a damper elastically disposed between the first connecting member and the second connecting member. The damper includes a damper body, a first fixed portion, and a second fixed portion. The first fixed portion and the second fixed portion are configured to connect with two opposite sides of the damper body, respectively. The first fixed portion includes an elastic ring sleeve configured to sleeve couple with the first connecting member. The second fixed portion is connected with the second connecting member.

CROSS-REFERENCE TO RELATED APPLICATIONS

This application is a continuation of application Ser. No. 16/255,599,filed on Jan. 23, 2019, which is a continuation application ofInternational Application No. PCT/CN2016/103164, filed on Oct. 25, 2016,which claims priority to Chinese Patent Application No. 201620812047.2,filed on Jul. 29, 2016, the entire contents of all of which areincorporated herein by reference.

TECHNICAL FIELD

The present disclosure relates to the technology field of aircrafts and,more particularly, to a damping structure for a gimbal assembly, agimbal assembly that includes the damping structure, and an unmannedaerial vehicle that includes the gimbal assembly.

BACKGROUND

In conventional designs of gimbals, damping structures such as dampingballs are typically adopted to suppress the vibration of the gimbals,thereby providing a stable gimbal for photographing. A damping ball istypically connected to a connecting member through a snap fit couplingstructure. However, because the damping ball is made of an elasticmaterial, the damping ball can separate from the connecting member whenthe damping ball deforms under a large force. As a result, the gimbalmay lose the damping effect and the photographing devices may bedamaged.

SUMMARY

According to a first aspect of the present disclosure, a dampingstructure configured to connect a gimbal with a carrier includes a firstconnecting member connectable with the gimbal. The damping structurealso includes a second connecting member connectable with the carrier.The damping structure also includes a damper elastically disposedbetween the first connecting member and the second connecting member.The damping structure further includes a separation-proof memberconnected with the damper and configured to cause the damper to abutagainst at least one of the first connecting member and the secondconnecting member through a stretching force generated by vibration ofthe damper.

According to a second aspect of the present disclosure, a gimbalassembly includes a gimbal configured to carry a load. The gimbalassembly also includes a damping structure configured to connect thegimbal with a carrier. The damping structure includes a first connectingmember connectable with the gimbal. The damping structure also includesa second connecting member connectable with the carrier. The dampingstructure also includes a damper disposed between the first connectingmember and the second connecting member. The damping structure furtherincludes a separation-proof member connected with the damper andconfigured to cause the damper to abut against at least one of the firstconnecting member and the second connecting member.

According to a third aspect of the present disclosure, an unmannedaerial vehicle includes an aircraft body and a gimbal assembly. Thegimbal assembly includes a gimbal configured to carry a load. The gimbalassembly also includes a damping structure configured to connect thegimbal with the aircraft body. The damping structure includes a firstconnecting member connectable with the gimbal. The damping structurealso includes a second connecting member connectable with the aircraftbody. The damping structure also includes a damper disposed between thefirst connecting member and the second connecting member. The dampingstructure further includes a separation-proof member connected with thedamper and configured to cause the damper to abut against at least oneof the first connecting member and the second connecting member.

BRIEF DESCRIPTION OF THE DRAWINGS

To better describe the technical solutions of the various embodiments ofthe present disclosure, the accompanying drawings showing the variousembodiments will be briefly described. As a person of ordinary skill inthe art would appreciate, the drawings show only some embodiments of thepresent disclosure. Without departing from the scope of the presentdisclosure, those having ordinary skills in the art could derive otherembodiments and drawings based on the disclosed drawings withoutinventive efforts.

FIG. 1 is a perspective view of an unmanned vehicle, according to anexample embodiment.

FIG. 2 is an enlarged perspective view of a gimbal assembly of theunmanned vehicle of FIG. 1, according to an example embodiment.

FIG. 3 is an exploded view of the gimbal assembly of FIG. 2 from anotherperspective, according to an example embodiment.

FIG. 4 is a cross-sectional view of a portion of the gimbal assembly ofFIG. 1, according to an example embodiment.

ELEMENTS LIST

Unmanned vehicle 1000 Aircraft body   1 Gimbal assembly   2 Dampingstructure  20 Connecting assembly  201 First connecting member  200Connecting plate 2000 Connecting arm 2004 First end 2005 Second end 2006Neck portion  2004a Through hole  2004b Second connecting member  204First connecting portion 2040 Second connecting portion 2042 Snap fithole  2042a Flange  2042b Resting surface  2042c Damper  202 Damper body2020 First through hole 2021 Second through hole 2023 First fixedportion 2022 Second fixed portion 2024 Snap-in portion  2024a Blockingportion  2024b Receiving hole 2026 Separation-proof member  206Insertion portion 2061 Head portion  2061a Abutting portion 2062 Gimbal 22 Connecting hole  220 Load  23 Details of the disclosed technicalsolution will be explained below with reference to the accompanyingdrawings.

DETAILED DESCRIPTION OF THE EMBODIMENTS

Technical solutions of the present disclosure will be described indetail with reference to the drawings, in which the same numbers referto the same or similar elements unless otherwise specified. It will beappreciated that the described embodiments represent some, rather thanall, of the embodiments of the present disclosure. Other embodimentsconceived or derived by those having ordinary skills in the art based onthe described embodiments without inventive efforts should fall withinthe scope of the present disclosure. In addition, when there is noobvious conflict, the following embodiments and the features included inthe embodiments can be combined.

As used herein, when a first component (or unit, element, member, part,piece) is referred to as “coupled,” “mounted,” “fixed,” “secured” to orwith a second component, it is intended that the first component may bedirectly coupled, mounted, fixed, or secured to or with the secondcomponent, or may be indirectly coupled, mounted, or fixed to or withthe second component via another intermediate component. The terms“coupled,” “mounted,” “fixed,” and “secured” do not necessarily implythat a first component is permanently coupled with a second component.The first component may be detachably coupled with the second componentwhen these terms are used. When a first component is referred to as“connected” to or with a second component, it is intended that the firstcomponent may be directly connected to or with the second component ormay be indirectly connected to or with the second component via anintermediate component. The connection may include mechanical and/orelectrical connections. The connection may be permanent or detachable.The electrical connection may be wired or wireless. When a firstcomponent is referred to as “disposed,” “located,” or “provided” on asecond component, the first component may be directly disposed, located,or provided on the second component or may be indirectly disposed,located, or provided on the second component via an intermediatecomponent. When a first component is referred to as “disposed,”“located,” or “provided” in a second component, the first component maybe partially or entirely disposed, located, or provided in, inside, orwithin the second component. The terms “perpendicular,” “horizontal,”“vertical,” “left,” “right,” “up,” “upward,” “upwardly,” “down,”“downward,” “downwardly,” and similar expressions used herein are merelyintended for describing relative positional relationships.

When a first item is fixedly coupled, mounted, or connected to a seconditem, the term “fixedly” means “securely,” and is relative to movably.When the first item is fixedly coupled, mounted, or connected to thesecond item, the first item does not move relative to the second item.The first item may be permanently coupled to the second item, or may bedetachably coupled to the second item. When a first item is “fixed” witha second item, the first item is securely connected with the seconditem. The connection may be permanent or detachable.

It should be understood that in the present disclosure, relational termssuch as first and second, etc., are only used to distinguish an entityor operation from another entity or operation, and do not necessarilyimply that there is an actual relationship or order between the entitiesor operations. The terms “comprising,” “including,” or any othervariations are intended to encompass non-exclusive inclusion, such thata process, a method, an apparatus, or a device having a plurality oflisted items not only includes these items, but also includes otheritems that are not listed, or includes items inherent in the process,method, apparatus, or device. Without further limitations, an itemmodified by a term “comprising a . . . ” does not exclude inclusion ofanother same item in the process, method, apparatus, or device thatincludes the item.

Unless otherwise defined, all the technical and scientific terms usedherein have the same or similar meanings as generally understood by oneof ordinary skill in the art. As described herein, the terms used in thespecification of the present disclosure are intended to describe exampleembodiments, instead of limiting the present disclosure. The term“and/or” used herein includes any suitable combination of one or morerelated items listed.

Further, when an embodiment illustrated in a drawing shows a singleelement, it is understood that the embodiment may include a plurality ofsuch elements. Likewise, when an embodiment illustrated in a drawingshows a plurality of such elements, it is understood that the embodimentmay include only one such element. The number of elements illustrated inthe drawing is for illustration purposes only, and should not beconstrued as limiting the scope of the embodiment. Moreover, unlessotherwise noted, the embodiments shown in the drawings are not mutuallyexclusive, and they may be combined in any suitable manner. For example,elements shown in one embodiment but not another embodiment maynevertheless be included in the other embodiment.

FIG. 1 shows an unmanned vehicle 1000 in accordance with an embodimentof the present disclosure. In some embodiments, the unmanned vehicle1000 may be any suitable type of unmanned aircraft, such as rotorcraft,fixed-wing aircraft, or an aircraft having a combined fixed-wing androtor. The rotor may be a single rotor, twin rotors, three rotors, fourrotors, six rotors, eight rotors, etc. In some embodiments, the unmannedvehicle may be an unmanned vehicle in the water (e.g., unmanned boat orship, unmanned submarine, etc.), an unmanned vehicle on the ground(e.g., driverless vehicle), an unmanned vehicle in the air (e.g.,unmanned aerial vehicle), etc. In some embodiments, the unmanned vehicle1000 may be an unmanned aerial vehicle (“UAV”). For convenience ofillustration, the UAV is used as an example of the unmanned vehicle inthe following discussion. Hence, the unmanned vehicle 1000 may also bereferred to as UAV 1000 for convenience of discussion. As shown in FIG.1, the UAV 1000 may include an aircraft body 1 and a gimbal assembly 2mounted on the aircraft body 1.

The aircraft body 1 may carry the gimbal assembly 2 coupled with theaircraft body 1. Thus, the aircraft body 1 is the carrier of the gimbalassembly 2. In some embodiments, the aircraft body 1 may include astructure having a hollow central portion. A plurality of devices orcomponents may be disposed inside the aircraft body 1, such as a circuitboard, a controller, sensors configured to measure the attitude of theUAV 1000 and information relating to the surrounding environment, suchas inertial measurement unit (“IMU”), altitude sensor, temperaturesensor, etc.

FIG. 2 shows that the gimbal assembly 2 may include a damping structure20, a gimbal 22, and a load 23. The damping structure 20 may be coupledwith the aircraft body 1 and the gimbal 22. In some embodiments, thedamping structure 20 may be entirely disposed inside the aircraft body1. The gimbal 22 may be configured to carry the load 23. The gimbal 22may be a single-axis gimbal, a dual-axis gimbal, or a three-axis gimbal.The gimbal 22 and the load 23 may be disposed outside of the aircraftbody 1. The load 23 may be any suitable devices that may be carried bythe gimbal 22, such as sensors and imaging devices. In some embodiments,the load 23 may include an imaging device, such as a camera.

FIG. 3 shows that the damping structure 20 may include one or moredampers 202 and a connecting assembly 201 configured to connect thegimbal assembly 2 and the aircraft body 1. The connecting assembly 201may include a first connecting member 200 and a second connecting member204. The first connecting member 200 may be coupled with the gimbalassembly 2, and the second connecting member 204 may be coupled with theaircraft body 1. The damper 202 may be configured to allow the firstconnecting member 200 to move relative to the second connecting member204 due to elastic deformation of the damper 202, thereby reducingvibrations.

In some embodiments, the first connecting member 200 may have a plateshape, including a connecting plate 2000 and two connecting arms 2004disposed at two opposite ends of the connecting plate 2000. In someembodiments, the connecting plate 2000 may include two longitudinalstrips separated at a distance. Thus, the weight of the connecting plate2000 may be reduced. Correspondingly, the weight of the first connectingmember 200 may also be reduced. In some embodiments, the strips of theconnecting plate 2000 may be disposed in parallel with one another andseparated at a distance from one another. In some embodiments, theconnecting plate 2000 may be disposed according to practical needs. Forexample, the number of the longitudinal strips included in theconnecting board 2000 may be changed. In some embodiments, the stripsmay be disposed to have a predetermined tilting angle between the strips(rather than being in parallel with one another). In some embodiments,the connecting plate 2000 may be an integral piece.

The two connecting arms 2004 may be respectively connected with twoopposite ends of the connecting plate. In some embodiments, eachconnecting arm 2004 may have a substantially longitudinal strip shape.Each connecting arm 2004 may include a first end 2005 and a second end2006 opposite the first end 2005. Each first end 2005 and each secondend 2006 may be connected with a damper 202. Each connecting arm 20004may include a neck portion 2004 a at locations adjacent the first end2005 and the second end 2006. In some embodiments, the neck portion 2004a includes a depressed portion on a side in the width direction. Thatis, the width of the neck portion 2004 a may be smaller than thecorresponding width of the first end 2005 or the corresponding width ofthe second end 2006. In some embodiments, both opposite sides in thewidth direction of each neck portion 2004 a may have depressed portions.Each neck portion 2004 a may be connected with a corresponding damper202. The depressed portion on each neck portion 2004 a may restrain thedamper 202 from being separated from the corresponding first end 2005 orthe second end 2006, thereby securely coupling the first connectingmember 200 and the damper 202.

In some embodiments, at least one of the connecting arms 2004 may becoupled with the gimbal 22. The connecting arm 2004 that is connectedwith the gimbal 22 may be provided with a through hole 2004 b. Thegimbal 22 may include a connecting hole 220 corresponding to eachthrough hole 2004 b. In some embodiments, the connecting hole 220 may bea threaded hole. The connecting arm 2004 may be fixedly connected withthe gimbal 22 through a bolt inserted into the through hole 2004 b andthreadedly coupled with the connecting hole 220. In some embodiments,the connecting arm 2004 may be connected with the gimbal using othersuitable methods, such as snap fit, gluing, riveting, welding,interference fit, etc. In some embodiments, the connecting arm 2004 andthe gimbal 22 may be integrally formed as a single piece.

In some embodiments, the connecting plate 2000 and the connecting arm2004 may be integrally formed. In some embodiments, various componentsof the first connecting member 200 may not be integrally formed. Rather,various components of the first connecting member 200 may be fixedtogether using any suitable methods, such as threaded coupling, snapfit, gluing, riveting, welding, and interference fitting, etc.

As shown in FIGS. 2-4, the second connecting member 204 may have asubstantially plate shape. The second connecting member 204 may includea first connecting portion 2040 and a second connecting portion 2042.The first connecting portion 2040 may be configured to connect thesecond connecting member 204 with the aircraft body 1. The secondconnecting portion 2042 corresponds to the damper 202, and may beconfigured to connect with the damper 202.

In some embodiments, the first connecting portion 2040 may be aprotruding column with an internal threaded hole. The protruding columnmay be formed on a surface of the second connecting member 204. In someembodiments, the first connecting portion 2040 may be formed on asurface of the second connecting member that faces against the firstconnecting member 200. In some embodiments, the first connecting portion2040 may be a cylindrical protruding column. In some embodiments, thefirst connecting portion 2040 may be other suitable shapes, such as aprismatic protruding column, an oval protruding column, a lumbar-shapedprotruding column, etc. In some embodiments, the first connectingportion 2040 may not be a protruding column. Instead, the firstconnecting portion 2040 may be a threaded hole directly disposed on thesurface of the second connecting member 204, and the aircraft body 1 mayhave a protruding column corresponding to the first connecting portion2040. When connecting with the aircraft body 1, the second connectingmember 204 may be fastened with the aircraft body 1 through a fastenerinserted through the first connecting portion, such as a threaded boltor a screw.

In some embodiments, the second connecting member 204 and the aircraftbody 1 may be connected using other suitable methods, such as snap fit,gluing, riveting, welding, and interference fitting, etc. In someembodiments, the second connecting member 204 and the aircraft body 1may be integrally formed.

In some embodiments, the second connecting portion 2042 may include asnap fit hole 2042 a corresponding to the damper 202, and a flange 2042b corresponding to the snap fit hole 2042 a. The snap fit hole 2042 a isconfigured to snap fit with the damper 202 to connect the damper 202with the second connecting member 204. In some embodiments, the snap fithole 2042 a may have a circular shape, although any other suitableshapes may be used, such as triangle, square, polygon, oval, and otherregular or irregular shapes.

In some embodiments, the flange 2042 b may protrude from a side surfaceof the second connecting member 204 that faces against the firstconnecting member 200. The flange 2042 b may surround the snap fit hole2042 a. The flange 2042 b may be separated from a circumferential edgeof the snap fit hole 2042 a at a predetermined distance. A restingsurface 2042 c may be provided between the flange 2042 b and thecircumferential edge of the snap fit hole 2042 a. In some embodiments,the flange 2042 b has a substantially circular ring shape. The flange2042 b may have other suitable shapes, such as oval ring shape, polygonring shape, etc. In some embodiments, the flange 2042 b may have acontinuous ring shape, or a non-continuous ring shape formed by aplurality of segments. The resting surface 2042 c may be at the sameheight as a side surface of the second connecting member 204 that facesagainst the first connecting member 200. In some embodiments, theresting surface 2042 c may be higher or lower than the side surface ofthe second connecting member 204 that faces against the first connectingmember 200. When the damper 202 snaps into the snap fit hole 2042 a, theflange 2042 b may contact a side of the corresponding damper 202,restraining the damper 202 from moving laterally relative to the secondconnecting member 204, thereby increasing the stability of theconnection between the second connecting member 204 and thecorresponding damper 202, and reducing the shaking between the secondconnecting member 204 and the corresponding damper 202.

In some embodiments, the flange 2042 b may be omitted.

In some embodiments, the damper 202 may include a damper body 2020, afirst fixed portion 2022, and a second fixed portion 2024. The firstfixed portion 2022 and the second fixed portion 2024 may be connectedwith two opposite sides of the damper body 2020, respectively. The firstfixed portion 2022 may be connected with the first connecting member200, and the second fixed portion 2024 may be connected with the secondconnecting member 204.

In some embodiments, the damper body 2020 may have a substantiallyspherical shape. The damper body 2020 may include a first through hole2021 and a second through hole 2023. The facing direction of the openingof the first through hole 2021 and the facing direction of the openingof the second through hole 2023 may be substantially perpendicular toone another. The center point of the first through hole 2021 and thesecond through hole 2023 may coincide with the center point of thedamper 202. The damper body 2020 may include multiple through holes toachieve better damping effect. The damper body 2020 may be made of asuitable material, such as an elastic material (e.g., rubber, silicone,etc.). In some embodiments, the damper body 2020 may have other shapes,such as a polygonal prism, an oval sphere, etc. In some embodiments, thefirst through hole 2021 and the second through hole 2023 may be omitted.In some embodiments, the damper body 2020 may include other throughholes in addition to the first through hole 2021 and the second throughhole 2023.

In some embodiments, the first fixed portion 2022 may be configured toconnect with the first end 2005 or the second end 2006 of the connectingarm 2004 of the first connecting member 200. The second fixed portion2024 may be configured to connect with the second connecting member 204.In some embodiments, the first fixed portion 2022 may be a ring sleevemade of an elastic material, which can be sleeve coupled to the firstend 2005 or the second end 2006, thereby fixedly connecting the damper202 with the first connecting member 200.

The second fixed portion 2024 may include a snap-in portion 2024 a and ablocking portion 2024 b connected with the snap-in portion 2024 a. Theblocking portion 2024 b may be connected with an end of the snap-inportion 2024 a that is distal from the damper body 2020. The size of theblocking portion 2024 b may be greater than the size of the snap-inportion 2024 a. The blocking portion 2024 b may form a protruding edgeprotruding from a circumferential side surface of the snap-in portion2024 a and located at the circumference of the snap-in portion 2024 a.In some embodiments, the size of the circumference of the snap-inportion 2024 a may be substantially the same as the size of thecorresponding snap fit hole 2042 a. In some embodiments, the snap-inportion 2024 a and the blocking portion 2024 b may both have asubstantially cylindrical shape. In some embodiments, the blockingportion 2024 b and the snap-in portion 2024 a may share a common axis.In some embodiments, the diameter of the blocking portion 2024 b may begreater than the diameter of the snap-in portion 2024 a. In someembodiments, the thickness of the blocking portion 2024 b and the heightof the flange 2042 b may be substantially the same. In some embodiments,the thickness of the blocking portion 2024 b may be slightly greaterthan the height of the flange 2042 b. In some embodiments, as shown inFIG. 4, a circumferential surface of the blocking portion 2024 b isconfigured to abut against an inner surface of the flange 2042 b of thesecond connecting member 204.

In some embodiments, the blocking portion 2024 b and the snap-in portion2024 a may have any suitable shapes, such as a prismatic protrudingcolumn, an oval protruding column, a lumbar-shaped protruding column,etc. In some embodiments, the blocking portion 2024 b and the snap-inportion 2024 a may have the same or different shapes.

In some embodiments, the first fixed portion 2022 and the second fixedportion 2024 may form an integral piece with the damper body 2020. Insome embodiments, the first fixed portion 2022 and the second fixedportion 2024 may be separately formed, and may be fixedly connected withthe damper body 2020 through a suitable connecting method, such asgluing, etc.

In some embodiments, the damping structure 20 may include aseparation-proof member 206. The separation-proof member 206 may beconfigured to restrain the corresponding damper 202 from separating fromthe second connecting member 204. Each separation-proof member 206 mayinclude an insertion portion 2061 and an abutting portion 2062 connectedwith the insertion portion 2061. In some embodiments, the insertionportion 2061 may have a substantially cylindrical shape, and theabutting portion 2062 may have a substantially circular plate shape. Thediameter of the abutting portion 2062 may be greater than the diameterof the insertion portion 2061, rendering the separation-proof member 206to have a substantially “T” shape. In some embodiments, the insertionportion 2061 and the abutting portion 2062 may have other shapes, whichmay be changed based on the practical needs. In some embodiments, thelength of the insertion portion 2061 may be smaller than the height ofthe damper 202. In other words, when the insertion portion 2061 isinserted into the damper 202, the insertion portion 2061 does notpenetrate throughout the damper 202. Therefore, the separation-proofmember 206 does not transfer vibration between the gimbal 22 and theaircraft body 1.

In some embodiments, the insertion portion 2061 may include a headportion 2061 a at an end distal from the abutting portion 2062. The headportion 2061 a may have a substantially spherical shape, and thediameter of the head portion 2061 a may be greater than the diameter ofthe insertion portion 2061. In some embodiments, the shape of theinsertion portion 2061 may be other shapes. Corresponding to theinsertion portion 2061, the damper 202 may include a receiving hole2026. The receiving hole 2026 may penetrate throughout the second fixedportion 2024 and extend into a portion of the damper body 2020. In someembodiments, the receiving hole 2026 may be connected and aligned withthe first through hole 2021 and the second through hole 2023. In someembodiments, the inner diameter of the receiving hole 2026 may beslightly smaller than the diameter of the insertion portion 2061. Whenthe insertion portion 2061 inserts into the receiving hole 2026, theouter surface of the insertion portion 2061 may tightly fit with theinner surface of the receiving hole 2026. The friction force between theouter surface of the insertion portion 2061 and the inner surface of thereceiving hole 2026 renders it difficult for the separation-proof member206 to exit from of the receiving hole 2026. The head portion 2061 a mayfurther restrain the separation-proof member 206 from being separatedfrom the receiving hole 2026.

In some embodiments, during assembling, the snap-in portion 2024 a maysnap-fit with the corresponding snap fit hole 2042 a, and the blockingportion 2024 b may rest on the resting surface 2042 c. Thecircumferential side surface of the blocking portion 2024 may abut on oragainst the inner surface of the flange 2042 b. Accordingly, the flange2042 b may restrain the lateral movement of the damper 202 relative tothe second connecting member 204. When the damper 202 stretches due tothe vibration, the blocking portion 2024 b may abut against the restingsurface 2042 c to restrain the second fixed portion 2024 from separatingfrom the second connecting member 204. The insertion portion 2061 of theseparation-proof member 206 may be inserted into the correspondingreceiving hole 2026 of the damper 202. The abutting portion 2062 mayabut against the surface of the blocking portion 2024 b. When the damper202 stretches due to vibration, the damper 202 may cause theseparation-proof member 206 to move together, which in turn causes theabutting portion 2062 to tightly abut against the blocking portion 2024b. As a result, the frictional resistance force experienced by theblocking portion 2024 b may increase, thereby restraining the blockingportion 2024 b from separating from the corresponding snap fit hole 2042a due to vibration. The disclosed structures may increase the stabilityand tightness of the connection between the second connecting member 204and the damper 202.

In some embodiments, the first fixed portion 2022 may have a structurethat is similar to the structure of the second fixed portion 2024, andthe first connecting member 200 may include structures similar to thestructures of the second connecting portion 2042.

The above described embodiments are exemplary embodiments of the presentdisclosure, and are not intended to limit the present disclosure. Allmodifications, equivalents, and improvements based on the spirit andprinciple of the present disclosure should fall within the scope ofprotection of the present disclosure.

What is claimed is:
 1. A damping structure configured for connecting agimbal with a carrier, comprising: a first connecting member connectablewith the gimbal; a second connecting member connectable with thecarrier; a damper disposed between the first connecting member and thesecond connecting member, the damper including: a damper body; a firstfixed portion including an elastic ring sleeve configured to sleevecouple with the first connecting member; and a second fixed portionconnected with the second connecting member, wherein the first fixedportion and the second fixed portion are configured to connect with twoopposite sides of the damper body, respectively.
 2. The dampingstructure of claim 1, wherein the damper includes a damping ball.
 3. Thedamping structure of claim 1, wherein the damper body has a sphericalshape.
 4. The damping structure of claim 1, wherein the damper bodyincludes a first through hole and a second through hole.
 5. The dampingstructure of claim 4, wherein: a facing direction of an opening of thefirst through hole and a facing direction of an opening of the secondthrough hole are perpendicular to one another; or a center point of thefirst through hole and the second through hole coincides with a centerpoint of the damper.
 6. The damping structure of claim 1, wherein thefirst connecting member includes a depressed portion, and the firstfixed portion is sleeve coupled with the first connecting member at thedepressed portion.
 7. The damping structure of claim 1, wherein: thesecond fixed portion includes a snap-in portion and a blocking portionconnected with the snap-in portion; the second connecting memberincludes a snap fit hole corresponding to the snap-in portion, thesnap-in portion being insertable into the snap fit hole; and theblocking portion extends into the snap fit hole and rests on a surfaceof the second connecting member to restrain the snap-in portion frombeing separated from the snap fit hole.
 8. The damping structure ofclaim 7, wherein: a size of the blocking portion is greater than a sizeof the snap-in portion; the blocking portion forms a protruding edgeprotruding from a circumferential side surface of the snap-in portionand located at the circumference of the snap-in portion; and theprotruding edge rests on the surface of the second connecting member. 9.The damping structure of claim 7, wherein: the second connecting memberincludes a flange corresponding to the snap fit hole, the flange of thesecond connecting member surrounding the snap fit hole; and acircumferential surface of the blocking portion is configured to abutagainst an inner surface of the flange of the second connecting member.10. The damping structure of claim 9, wherein: a thickness of theblocking portion is the same as a height of the flange of the secondconnecting member, or the thickness of the blocking portion is greaterthan the height of the flange of the second connecting member.
 11. Thedamping structure of claim 1, further comprising: a separation-proofmember connected with the damper and configured to cause the damper toabut against at least one of the first connecting member or the secondconnecting member through a stretching force generated by vibration ofthe damper.
 12. The damping structure of claim 11, wherein: theseparation-proof member includes an insertion portion and an abuttingportion connected with the insertion portion; the insertion portion isconfigured to insert into the damper body; and the abutting portion isconfigured to abut against the damper body, such that the damper bodyabuts against the second connecting member due to a stretching forcecaused by vibration of the damper body.
 13. The damping structure ofclaim 12, wherein: the damper body includes a receiving hole penetratingthroughout the second fixed portion and extending into the damper body;and the insertion portion is inserted into the receiving hole andfrictionally contacts an inner surface of the receiving hole.
 14. Thedamping structure of claim 12, wherein a length of the insertion portionis smaller than a height of the damper.
 15. The damping structure ofclaim 12, wherein: the insertion portion includes a head portion formedat an end of the insertion portion distal from the abutting portion; asize of the head portion is greater than a size of the insertionportion; and the head portion is frictionally coupled with the damper.16. A gimbal assembly, comprising: a gimbal configured to carry a load;and a damping structure configured to connect the gimbal with a carrier,the damping structure including: a first connecting member connectablewith the gimbal; a second connecting member connectable with thecarrier; a damper disposed between the first connecting member and thesecond connecting member, the damper including: a damper body; a firstfixed portion including an elastic ring sleeve configured to sleevecouple with the first connecting member; and a second fixed portionconnected with the second connecting member, wherein the first fixedportion and the second fixed portion are configured to connect with twoopposite sides of the damper body, respectively.
 17. The gimbal assemblyof claim 16, wherein the damper structure further includes: aseparation-proof member connected with the damper and configured tocause the damper to abut against at least one of the first connectingmember or the second connecting member through a stretching forcegenerated by vibration of the damper.
 18. The gimbal assembly of claim16, wherein: the second fixed portion includes a snap-in portion and ablocking portion connected with the snap-in portion; the secondconnecting member includes a snap fit hole corresponding to the snap-inportion, the snap-in portion being insertable into the snap fit hole;and the blocking portion extends into the snap fit hole and rests on asurface of the second connecting member to restrain the snap-in portionfrom being separated from the snap fit hole.
 19. An unmanned aerialvehicle, comprising: an aircraft body; and a gimbal assembly, including:a gimbal configured to carry a load; and a damping structure configuredto connect the gimbal with the aircraft body, the damping structureincluding: a first connecting member connectable with the gimbal; asecond connecting member connectable with the aircraft body; a damperdisposed between the first connecting member and the second connectingmember, the damper including: a damper body; a first fixed portionincluding an elastic ring sleeve configured to sleeve couple with thefirst connecting member; and a second fixed portion connected with thesecond connecting member, wherein the first fixed portion and the secondfixed portion are configured to connect with two opposite sides of thedamper body, respectively.
 20. The unmanned aerial vehicle of claim 19,wherein the damper structure further includes: a separation-proof memberconnected with the damper and configured to cause the damper to abutagainst at least one of the first connecting member or the secondconnecting member through a stretching force generated by vibration ofthe damper.